CAE SimuFlite Citation Bravo, Руководство по подготовке пилотов

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Flight Planning
Citation Bravo
Developed for Training Purposes
4-71
September 2005
CAE SimuFlite
Obstacle Clearance Diagram
4,800 FT (0 )
400
300
200
100
35
0
1,000 2,000 5,000 6,000 7,000 8,000
REFERENCE ZERO
6.2% @ 0 FLAPS
O
5.3% @ 15 FLAPS
O
290 FT
4,200 FT (15 )
O
3,000 4,000
1,100 FT
500 FT
O
5,300 FT (RUNWAY)
4,800 FT
5,300 FT
5,900 FT
4-36
Single Engine Takeoff Flight Path Table
An alternate method to determine obstacle clearance is to use
the Single Engine Takeoff Flight Path table (
Figure 4-37
).
These tabulated charts in the AFM compare known obstacle
heights with various climb gradients to determine the computed
distance to clear an obstruction. Each distance is from reference
zero; the pilot must compute the “run” distance to the obstacle
to compare it with the charted value. Use the full obstacle
height because the charts were created with the 35 ft reference
zero as part of the equation.
The chart is limited to 50 ft increments in obstacle heights and
is not computed for net climb gradients less than 3%. FAR 25
requires an aircraft capability of at least a 2.4% climb gradient
for takeoff. The 2.4% climb gradient is a gross climb gradient.
Net climb gradients are gross climb gradients reduced by 0.8%
in the second segment climb.
Single Engine Takeoff Flight Path
Use the Single Engine Takeoff Flight Path table to determine
the climb gradient required to clear the obstacle with one engine
operating.
The 325-ft obstacle is 5,900 ft from reference zero (flaps 15°)
and 5,300 feet from reference zero (flaps 0°).
Enter the table at either the obstacle’s height ( 325 ft ) or the
computed required gradient.
For flaps 0°, a 325-ft obstacle is cleared in 5,035 ft with a
6.2% gradient.
For flaps 15°, a 325-ft obstacle is cleared in 5,970 ft with a
5.3% gradient.
This confirms the calculated figures using the rise over run
formula that the obstacle must be cleared using the 0° flap
configuration.
When using the single engine takeoff flight path chart, it may
initially appear that a 15° flap aircraft performs better in the
climb than a 0° flap aircraft; however, for both aircraft to
have the same gradient, the 15° flap aircraft must weigh less
than the 0° aircraft. Therefore the 15° flap distance is
shorter because the aircraft’s weight is lighter.
When comparing flap setting performance for both aircraft
at the same weight and atmospheric conditions, remember
that a flaps 15° aircraft always requires a shorter takeoff
field length; a flaps 0° always requires a greater climb
gradient.
4-72